Systems and devices for remotely operated unmanned aerial vehicle report-suppressing launcher with portable rf transparent launch tube

ABSTRACT

An unmanned aerial vehicle (UAV) launch tube that comprises at least one inner layer of prepreg substrate disposed about a right parallelepiped aperture, at least one outer layer of prepreg substrate disposed about the right parallelepiped aperture, and one or more structural panels disposed between the at least one inner layer of prepreg substrate and the at least one outer layer of prepreg substrate. An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a continuation of patent application Ser. No.17/728,603, filed Apr. 25, 2022, which is a continuation of patentapplication Ser. No. 16/920,578, filed Jul. 3, 2020, which issued asU.S. Pat. No. 11,319,087 on May 3, 2022, which is a continuation ofpatent application Ser. No. 16/574,344, filed Sep. 18, 2019, whichissued as U.S. Pat. No. 10,703,506 on Jul. 7, 2020, which is acontinuation of patent application Ser. No. 16/137,196 filed Sep. 20,2018, which issued as U.S. Pat. No. 10,450,089 on Oct. 22, 2019, whichis a continuation of patent application Ser. No. 14/887,675 filed Oct.20, 2015, which issued as U.S. Pat. No. 10,124,909 on Nov. 13, 2018,which is a continuation of patent application Ser. No. 13/234,044, filedSep. 15, 2011, which issued as U.S. Pat. No. 9,187,184 on Nov. 17, 2015,which is a continuation of patent application Ser. No. 13/229,377, filedSep. 9, 2011, which issued as U.S. Pat. No. 8,505,430 on Aug. 13, 2013,which is a continuation of International Application No.PCT/US2010/048313, filed Sep. 9, 2010, which claims priority to and thebenefit of U.S. Provisional Patent Application Ser. No. 61/240,996 filedSep. 9, 2009, U.S. Provisional Patent Application Ser. No. 61/240,987filed Sep. 9, 2009, and U.S. Provisional Patent Application Ser. No.61/241,001 filed Sep. 9, 2009, all of which are hereby incorporatedherein by reference in their entirety for all purposes.

TECHNICAL FIELD

Embodiments include launch tubes and canisters, report-suppressinglaunch tubes, and sabots for an unmanned aerial vehicle (UAV).Embodiments also pertain to systems comprising one or more UAVs, and toa system comprising a command node and a launcher containing a UAV in apre-launch state configured to receive command signals from the commandnode.

BACKGROUND

Typically UAVs are shipped to a launch site in an unassembled state. Atthe site they are assembled, tested, and then launched. Launching istypically executed by hand, by an elastic tether, a powered wench, froma moving vehicle, or some combination thereof. Such methods can be timeconsuming and/or cumbersome. Once launched, a UAV may receive uplinksand may be guided by a human-in-the-loop, a human intermittentlyup-linking course corrections, e.g., via supervisory control, or by apreloaded intercept/strike point in combination with an onboard flightpath guidance generator and outputs of inertial sensors and/or from aGlobal Positioning System (GPS) receiver.

SUMMARY

Embodiments may include articles such as an unmanned aerial vehicle(UAV) launch tube comprising: (a) at least one inner layer of prepregsubstrate disposed about a right parallelepiped aperture; (b) at leastone outer layer of prepreg substrate disposed about the rightparallelepiped aperture; and (c) one or more structural panels disposedbetween the at least one inner layer of prepreg substrate and the atleast one outer layer of prepreg substrate. The at least one inner layerof prepreg substrate may comprise epoxy prepreg Kevlar™ or other lightweight composites. The at least one outer layer of prepreg substrate maycomprise epoxy prepreg Kevlar™ or other light weight composites. The oneor more structural panels may comprise balsawood or a light weightcomposite. In some embodiments, the one or more structural panels maycomprise four structural panels, where each panel comprises acylindrical segment, and each panel has a planar surface defined by achord length and a cylindrical height. Each proximate planar surface maybe disposed orthogonally relative to one another, each structural panelhaving a first lateral edge and a second lateral edge perpendicular tothe chord length, where the first lateral edge of a first structuralpanel is proximate to, but not contacting, a first lateral edge of asecond structural panel. The second lateral edge of the first structuralpanel may be proximate to, but not contacting, a first lateral edge of athird structural panel. The first lateral edge of a fourth structuralpanel may be proximate to, but not contacting, a second lateral edge ofa second structural panel. The second lateral edge of the fourthstructural panel may be proximate to, but not contacting, a secondlateral edge of a third structural panel, where the planar surfaces ofeach of the four structural panels may be aligned with a launch tubecenterline. In addition, each of the four structural panels may bedisposed between the inner layer of epoxy prepreg substrate and theouter layer of epoxy prepreg substrate. Embodiments include articlessuch as an unmanned aerial vehicle (UAV) launch tube configured forreport suppression comprising a structural element configured to engagethe UAV within a launcher volume defined by an inner wall. The articlemay be dimensioned to provide a pressure seal at the inner wall andtethered to the inner wall. The structural element may have a hollow, orcavity, having an open end oriented toward a high pressure volume and atether attached within a hollow or cavity of the article and may beattached to the inner wall retaining the high pressure volume.

Additional embodiments may include methods and UAV systems comprising:(a) a communications node; and (b) a launcher comprising a UAVconfigured to receive, in a pre-launch state, command inputs from thecommunications node. In some embodiments, the UAV in a pre-launch stateis further configured to transmit to a communications node UAV statusdata responsive to a received query signal. In some embodiments, the RFantenna of the UAV is contained within the launcher volume. In someembodiments, the launch propulsion system is configured to receive RFsignals.

BRIEF DESCRIPTION OF THE DRAWINGS

Embodiments are illustrated by way of example and not limitation in thefigures of the accompanying drawings, and in which:

FIG. 1 is a top-side perspective view of an exemplary launch tubeembodiment;

FIG. 2 is a bottom-side perspective view of a portion of an exemplarylaunch tube embodiment;

FIG. 3 is cross-sectional view of an exemplary launch tube embodiment;

FIG. 4 is an exemplary depiction of a launch tube configured as a UAVcarrying case embodiment of the present invention;

FIG. 5 is an exemplary depiction of a launch tube configured as a UAVcarrying case embodiment of the present invention;

FIG. 6 is an exemplary depiction of a launch tube configured as a UAVcarrying case embodiment with support struts and footing deployed;

FIG. 7 is a top-side perspective view of an exemplary tethered sabotembodiment of the present invention;

FIG. 8 is a top view of an exemplary tethered sabot embodiment of thepresent invention;

FIG. 9 is a cross-sectional view of an exemplary tethered sabotembodiment of the present invention;

FIGS. 10A-10E depict an exemplary UAV launch using a tethered sabotembodiment of the present invention;

FIGS. 11A-11B depict, in a cross-sectional view of the distal end of alunch tube, an exemplary UAV launch using a tethered sabot embodiment ofthe present invention;

FIG. 12A is a bottom-side perspective view of an exemplary UAV in apre-launch state;

FIG. 12B depicts an exemplary UAV with its airfoils deployed and itspusher propeller rotating;

FIG. 13 is a bottom-side perspective view of a portion of an exemplarylaunch tube embodiment;

FIG. 14 depicts an exemplary functional block diagram of the UAVprocessing and guidance and control subsystem; and

FIG. 15 is a top-level system architecture of a system embodiment.

DETAILED DESCRIPTION

FIG. 1 is a top-side perspective view of an exemplary launch tube 100embodiment. The top, or open end 110, of the exemplary launch tubepresents a square-shaped aperture having rounded corners. Disposedbetween an outer layer of prepreg substrate 120 and an inner layer ofprepreg substrate 130 are four structural panels 141-144.

FIG. 2 is a bottom-side perspective view of a portion of an exemplarylaunch tube embodiment 200. The bottom, or closed end 210, of theexemplary launch tube presents an end 220 curved about an axis collinearwith a first footing pivot point protrusion 230 where a second footingpivot point protrusion is opposite the first footing pivot pointprotrusion 230, but not shown in the figure.

FIG. 3 is a cross-sectional view 300 of the exemplary launch tubeembodiment of FIG. 1 showing four structural panels 141-144 disposedabout a launch tube centerline. A non-cylindrical UAV may be placed andlaunched from such a volume. Each panel is shown having an outer surfacecurvature 311 representative of a radius of curvature 322 greater thanthe distance 323 from the outer surface 350 to the launch tubecenterline 360. Each panel 141-144 is shown having a planar innersurface 312 representative of a chord length 313. Accordingly, an endface 314 of each panel 141-144 in the present cross-sectional view is acircular segment. Each panel is shown disposed between an inner layer ofprepreg substrate 370 and an outer layer of prepreg substrate 380. Thepanels are shown disposed apart from one another, with there being space390 between the lateral edges 318, 319 of the panels. Accordingly, theinner layer of prepreg substrate 370 and the outer layer of prepregsubstrate 380 contact one another at the corners 301-304 of the rightparallelepiped-shaped volume 305. The outer layer of prepreg substrate380 defines in cross-sectional view, a substantially ovoid-shapedoutside perimeter. In some embodiments the inner layer 370 and outerlayer 380 may comprise epoxy prepreg Kevlar™ or a composite material, orcombinations of both, and the structural panels may comprise balsawoodor a light weight composite material, or combination of both.

FIG. 4 is an exemplary depiction of a launch tube configured as a UAVcarrying case 400 embodiment. A footing 410 is shown rotatably attachedto the launch tube 405 via a footing pivot point protrusion 230. A firststrut or leg 420 is shown rotatably attached to the launch tube 405proximate to the top 110 of the launch tube. A second strut or leg isdisposed opposite the first strut and is not shown in this figure. A cap430 is shown covering the otherwise open end of the launch tube and isshown restrained by a circumferential strap 431.

FIG. 5 is an exemplary depiction of a launch tube configured as a UAVcarrying case embodiment in a partially deployed state. That is, the cap430 is shown removed, exposing the open end of the launch tube that mayhave an optional membrane seal 540 as shown. The seal 540 may be afrangible film applied to repel sand, soil, moisture, and/or grit fromentering the launch tube during pre-launch preparations. The footing 410is shown partially rotated away from the launch tube and the first strutor leg 420 is shown partially rotated into a support position.

FIG. 6 is an exemplary depiction of a launch tube 600 configured as aUAV carrying case embodiment with support struts 420 and footing 410deployed. The use of the term “tube” is done so with the intent toindicate a volume from which a UAV may be launched and not to limit theshape of the volume to a cylindrical tube. The angle 610 of the pair ofstruts or pair of legs may be adjusted to accommodate a desired launchangle 601 relative to local level 602. Likewise, the angle 620 betweenthe launch tube and the footing may be adjusted to accommodate thedesired launch angle 601. In some embodiments, the pair of struts orpair of legs 420 may comprise segments of differing diameters allowingfor a telescoping of the distal segment 422 into and out of the proximalsegment 421. In these embodiments, the overall length of the legs may beadjusted, either to accommodate uneven local terrain, and to accommodatea desired launch angle 601, or both. The footing 410 may be sized toreceive the down force from a boot and/or a mass to further enhance thestiction between the lower surface of the footing and the local groundsurface 602. The top of the launch tube 630 may include a frangiblemembrane to protect the internal launcher volume from grit, sand,moisture and the effects of weather. Once the launcher is positioned ona surface, the launcher 600 may be remotely controlled for purposes ofuploading mission information to the UAV while the UAV is in apre-launch state and for purposes of receiving UAV status information.

Embodiments include an unmanned aerial vehicle (UAV) launch tube thatmay comprise a tethered sabot configured to engage a UAV within alauncher volume defined by an inner wall, the tethered sabot dimensionedto provide a pressure seal at the inner wall, and tethered to the innerwall. In some embodiments, the tethered sabot may be hollow having anopen end oriented toward a high pressure volume and a tether attachedwithin a hollow of the sabot and attached to the inner wall retainingthe high pressure volume.

For a launcher having a right parallelepiped aperture, an exemplarytethered sabot 700 embodiment as depicted in FIG. 7 may be used. Thesabot may be made of carbon fiber, e.g., a prepreg carbon fiber shapedover a form and cured to yield a hollow article, open at one end. Thesabot may have a channel 710 for receiving a pusher propeller assemblyof a UAV. The sabot may also have a depression 720 for receiving gasoutside of the volume provided by the hollow. The sabot is showndepicting an end portion 730 of a structural element that may span thewidth of the sabot to provide for a structural attachment for a tether.A portion of a tether 740 is shown extending from the hollow of thesabot.

FIG. 8 is a top view of an exemplary tethered sabot 700 embodiment. Thestructural element 810 may be a rod, and may span the width of the sabot700. A loop portion 820 of the tether may engage the structural element810. The tether 740 may be silicone prepreg, braided Kevlar™ where anend of the tether 740 may be tucked within the braiding of the tether740 after looping the structural element 810 and further cured.

FIG. 9 is a cross-sectional view of the sabot 700 taken from the topview of FIG. 8 depicting the tether 740 engaging the structural element810 within the hollow 910 of the sabot 700.

FIG. 10A illustrates a cross-sectional view of a loaded launcher 1010,such as the launcher depicted in FIGS. 1 and 2 ; loaded with a UAV 1020such as the UAV depicted in FIG. 3 . In this example, the launcher 1010is shown having an optional frangible seal 1030. Two gas-generatingcanisters 1041, 1042 are shown disposed within the aft volume 1001 ofthe launcher 1010. An exemplary tethered sabot 1050 is shown disposedbetween the gas-generating canisters 1041, 1042 and the UAV 1020.

FIG. 10B illustrates, in the cross-sectional view of FIG. 10A, a firstgas-generating canister 1041 increasing the pressure—as depicted by thesmoke cloud 1002—within the volume 1001 between the inner aft wall 1011of the launcher 1010 and the sabot 1050. The tether 1060 may be attachedto the inner base wall 1013 via a tether reel or winding element 1014.Relative to FIG. 10A, the sabot 1050 is shown displaced along the launchtube—in this example a right parallelepiped volume—and moving with itthe UAV 1020. The UAV is shown breaking the frangible seal 1030 andbeginning to exit the launcher 1010.

FIG. 10C illustrates, in the cross-sectional view of FIG. 10A, thesecond gas-generating canister 1042 increasing, or sustaining, thepressure (as depicted by the second smoke cloud 1003) within the volumebetween the inner aft wall 1012 of the launcher 1010 and the sabot 1050.The sabot 1050 is shown displaced further along the launch tube, thetether 1060 is shown in a payout length, and, moved with the sabot 1050,the UAV 1020 is shown substantially outside of the launcher.

FIG. 10D illustrates, in the cross-sectional view of FIG. 10A, the sabot1050 fully displaced within the launch tube, constrained from furthertravel by the tether 1060, and retaining the gas within the launchervolume.

FIG. 10E illustrates, in the cross-sectional view of FIG. 10A, the sabot1050 fully displaced within the launch tube, constrained from furthertravel by the tether 1060, and retaining the gas within the launchervolume and allowing the seeping 1090 of gas from the launcher volumeinto the surrounding atmosphere.

FIG. 11A depicts, a cross-sectional view of the distal, an unsealed, endof a lunch tube 1100, as the sabot 1050 approaches full payout asdepicted in FIG. 10D. In some embodiments using hot or warm gasgenerators, the sabot 1050 travels approximately no further than thelocation depicted in FIG. 11A, and a seepage of gas to atmosphere isaround the sabot as the sabot may shrink in a cooling cycle from havingbeen heated by the gas. In some embodiments using warm or cool gasgenerators, the sabot 1050 may travel to partially extend from the rim1120 of the launcher (FIG. 11B) where gas may seep 1110 from the sidedepression 720 once the sabot lip 701 has cleared the launcher rim 1120.By retaining the sabot 1050 via the tether 1060, the launcher retains,for a brief period, a substantial portion of the pressure waves, i.e.,the report, and heat produced by rapid gas generation. Post-launch, thelauncher diffuses the pressure from the launcher via seepage about thesabot 1050.

In some embodiments, the sabot 1050 may expand out to contact the innerwall or walls of the launcher due to the pressure exerted on theinterior of the sabot 1050 by the gas from the gas generators. Thisexpansion can cause, or at least facilitate, the formation of a sealbetween the sabot 1050 and the inner wall or walls and in doing soprevent or limit the passage of gas around the sabot 1050 during itsmovement along the tube. In certain embodiments, the sabot may beconfigured to form gaps between the sabot and the inner wall or innerwalls of the launcher. The size of such gaps may be set to provide adesired amount of gas leakage. In some embodiments, the sabot 1050 maybe sized to allow enough gas leakage to prevent the launcher frombecoming too hot from containing the launch gases such that thestructural integrity of the launcher is compromised or breached.Accordingly, sabot 1050 embodiments may be sized to limit gas leakage tolimit the sound propagation of the sonic waves generated during thelaunch process.

FIG. 12A depicts, in a bottom-side perspective view, an exemplary UAV ina pre-launch state 1200, i.e., with its wing 1210 and tail surfaces 1220folded beneath the fuselage of the vehicle. Also shown is a propellerhub 1230 about which a propeller may be rotatably mounted. The airvehicle may include a radio frequency (RF) antenna 1231 conformal withor extending from the vehicle. Whether the tube volume is a rightcylinder, a right parallelepiped, or some other shape, the cross-sectionor cross-sections of the UAV may be insufficient to maintain anair-tight fit between the vehicle and the inner walls of the launcher.Accordingly, for launches based on gas pressure, a sabot may be disposedbetween the gas source and the UAV. FIG. 12B depicts an exemplary UAV ina launched state 1201 with its airfoils 1210, 1220 deployed and itspusher propeller 1232 rotating.

FIG. 13 is a side elevational view of the air vehicle 1300 embodimentloaded into a forward portion of a launcher 1310. The aft portion of thelauncher 1320 is shown having a pair of gas-generating canisters 1331,1332 and may include an RF antenna 1333 and receiver unit 1334, and apower source 1336, such as a battery for powering the launcher. In someembodiments the power source 1336 can also power the UAV 1300 while itis in the launcher 1310, allowing for maximum battery life for the UAV'sbattery after leaving the launcher 1310. Balsawood and epoxy prepregKelvar™ are examples of structural elements having high RF permeability.Accordingly, RF antenna and receiver elements of the UAV and/or RFantenna and receiver elements of the launch propulsion unit may receiveRF commands from a command node with negligible signal attenuation dueto the launcher structure.

FIG. 14 depicts an exemplary functional block diagram of the UAVprocessing and guidance and control subsystem 1400 where the guidancesensor 1414 provides information about the external environmentpertaining to seeking processing of a seeker processing 1420. A guidancesensor 1414, and more generally, a guidance sensor suite, may include apassive and/or active radar subsystem, an infrared detection subsystem,an infrared imaging subsystem, a visible light imaging subsystem such asa video camera-based subsystem, an ultraviolet light detectionsubsystem, and combinations thereof. The seeker processing 1420 mayinclude both image processing and target tracking processing, and targetdesignation or re-designation input 1421 that may be received from anuplink receiver 1435 and/or as an output of a guidance process 1430. Theimage processing and/or target tracking information 1422 may betransmitted via a downlink transmitter 1423, which may be a part of anuplink/downlink transceiver. The guidance processor 1430, in executinginstructions for guidance processing, may take in the target information1424 from the seeker processing 1420, and UAV flight status informationsuch as position, velocity and attitude from the GPS receiver 1431, andgyroscopes and accelerometers 1432, if any. Once in flight, the guidanceprocessor 1430, to receive reconnaissance waypoints and/or surveillanceoptimizing trajectories, may reference a memory store 1433. For systemembodiments, the guidance process 1430 may receive, by way of anexternal data port 1434, e.g., during a pre-launch phase, or by way ofan uplink receiver 1435, e.g., during a post-launch phase, receiveand/or upload reconnaissance waypoints and/or surveillance optimizingtrajectories. The guidance processor 1430, as part of executinginstructions for determining flight path, a trajectory, or a coursesteering angle and direction, may reference the waypoint and/orsurveillance optimizing trajectory information, particularly when not ina terminal homing mode. The guidance processor 1430 may receive acommand via an uplink receiver 1435 to set an initial post-launch modeor flight plan. The uplink receiver 1435 may receive commands, targetdata, and or flight plan information from a communications node whilethe UAV is in a pre-launch state.

An example of a terminal homing mode may be proportional navigation witha gravity bias for strike sub-modes of the terminal homing mode, and anacceleration bias for aerial intercept sub-modes of the terminal homingmode. The guidance processing 1430 and autopilot processing 1440 mayexecute instructions to effect a bank-to-turn guidance, for example, inan elevon embodiment, to redirect the air vehicle by re-orienting itsvelocity vector. For example, one or more control surfaces may bere-oriented via one or more control surface actuators 1450 causingforces and torques to reorient the air vehicle and the portion of itslinear acceleration that is orthogonal to its velocity vector. Theportion of the linear acceleration of the air vehicle that is along thevelocity vector is greatly affected by aerodynamic drag, and the linearacceleration may be increased via a motor processor 1460 and a propellermotor 1470. For embodiments with full three-axis control, additionalcontrol topologies may be implemented including skid-to-turn and otherproportion-integral-differential guidance and control processingarchitectures as well. The seeker processing 1420, guidance processing1430, motor processing 1460, and/or autopilot processing 1440 may beexecuted by a single microprocessor having addressable memory and/or theprocessing may be distributed to two or more microprocessors indistributed communication, e.g., via a data bus.

FIG. 15 is a top-level system architecture of a system 1500 embodiment.Ground vehicles 1501, aircraft 1502, spacecraft 1503, airbornesurveillance or airborne communication nodes 1504, or ground,human-portable, communication nodes 1505 may transmit command signalsvia an RF link 1511-1515 to a launcher 1520 embodiment, that may be, forexample, the embodiment depicted in FIG. 13 . In some embodiments, theUAV, in a pre-launch state, may output along an RF link 1511-1515 to arequesting node 1501-1505, status information, e.g., battery levels, andthe results of self-diagnostics. Launcher embodiments provide for aself-contained RF node via the UAV contained in the launcher. Forexample, the UAV may be placed in a standby mode, and remain responsiveto a received RF signal that may command a full power-up, and thereafterthe UAV in the launcher may be ready to be committed to launch—e.g., byan RF command of an offsite command node. The self-containedlauncher-UAV may be deployed and left at a prospective launch site for aprotracted period of time, and thereafter may be powered up and launchedresponsive to one or more command signals from an offsite or otherwiseremotecommand node.

It is contemplated that various combinations and/or sub-combinations ofthe specific features and aspects of the above embodiments may be madeand still fall within the scope of the invention. Accordingly, it shouldbe understood that various features and aspects of the disclosedembodiments may be combined with or substituted for one another in orderto form varying modes of the disclosed invention. Further it is intendedthat the scope of the present invention herein disclosed by way ofexamples should not be limited by the particular disclosed embodimentsdescribed above.

What is claimed is:
 1. A method comprising: receiving, by a receiverdisposed within a launcher, wireless communication via one or moreradio-frequency (RF) signals received wirelessly through a launcher wallof the launcher, wherein the launcher wall comprises an RF permeablematerial; and commanding, by the launcher, an unmanned aerial vehicle(UAV) disposed within the launcher to enter a standby mode whileremaining responsive to received RF signal commands for a full power-up.2. The method of claim 1, wherein the command the enter the standby modeprovides a self-contained launcher-UAV configured to be deployed andleft at a prospective launch site for a protracted period of time. 3.The method of claim 1, wherein the UAV is configured to be powered upand launched responsive to one or more command signals from an offsitenode.
 4. The method of claim 3, further comprising: transmitting, by atransmitter disposed within the launcher, wireless communication via oneor more RF signals, based on the offsite node requesting statusinformation while in a pre-launch state, wherein the status informationis associated with the UAV.
 5. The method of claim 1, wherein thewireless communication via one or more RF signals is transmitted from atleast one of: a ground vehicle, an aircraft, a spacecraft, an airbornesurveillance node, an airborne communication node, and a groundcommunication node.
 6. The method of claim 1, wherein the received oneor more RF signals are received by an RF antenna disposed within thelauncher.
 7. The method of claim 1, further comprising: transmitting, byan external communications node, the one or more RF signals received bythe receiver disposed within the launcher.
 8. The method of claim 1,wherein the one or more RF signals received by the receiver comprise atleast one of: a reconnaissance waypoint information, a surveillanceoptimizing trajectory information, a target data, and a flight planinformation.
 9. The method of claim 1, wherein the received RF signalcommands for a full power-up configures the UAV in the launcher to beready to be committed to launch.
 10. The method of claim 1, furthercomprising: generating gas by one or more gas generating canistersduring a launch of the UAV disposed within the launcher; and retainingthe generated gas within the launcher after the launch of the UAV.
 11. Asystem comprising: a launcher having a launcher wall, the launcher wallhaving radio-frequency (RF) permeability; an unmanned aerial vehicle(UAV) disposed within the launcher; and a receiver disposed within thelauncher, the receiver receiving wireless communication via one or moreRF signals received wirelessly through the launcher wall.
 12. The systemof claim 11, wherein the launcher provides a self-contained launcher-UAVconfigured to be deployed and left at a prospective launch site for aprotracted period of time.
 13. The system of claim 11, wherein the UAVcommands a full power-up responsive to the received wirelesscommunication.
 14. The system of claim 13, wherein the UAV commits to alaunch responsive to the received wireless communication.
 15. The systemof claim 11, wherein the wireless communication via one or more RFsignals is transmitted from at least one of: a ground vehicle, anaircraft, a spacecraft, an airborne surveillance node, an airbornecommunication node, and a ground communication node.
 16. The system ofclaim 11 further comprising: a transmitter disposed within the launcher,the transmitter transmitting wireless communication via one or more RFsignals transmitted wirelessly through the launcher wall.
 17. The systemof claim 11, wherein the receiver further comprises an RF antennadisposed within the launcher.
 18. The system of claim 11, wherein thereceiver is in communication with an external communications node, in apre-launch state, to wirelessly receive one or more RF signals from theexternal communications node.
 19. The system of claim 11, wherein thereceived one or more RF signals comprise at least one of: areconnaissance waypoint information, a surveillance optimizingtrajectory information, a target data, and a flight plan information.20. The system of claim 11, wherein the launcher further comprises: amembrane seal disposed over an open end of the launcher preventingoutside elements from entering the launcher prior to launch; and one ormore gas generating canisters disposed within the launcher, wherein theone or more gas generating canisters generate gas during a launch of theUAV disposed within the launcher, and wherein the generated gas isretained within the launcher after the launch of the UAV.